Fuselage fitting



Dec. 16, 1930. v 5, CAPRONI 1,785,615

FUSELAGE FITTING Filed Dec. 5. 1929 2 Sheets-Sheet l INVENTOR 3 -Caproz zi,

ATTORN EY 'Patentecl Dec. 16, 1 9,30

PATENT OFFICE GIANNI CAPRONI, OEROME, ITALY FUSELAGE FITTING I Application filed December 5, 1929, Serial No. 411,942, and in Italy December 10, 1 928.

The object of the present invention is an attachment particularly intended to connect the longitudinal, transversal and diagonal elements of the tubular structures used in aeronautical constructions;

, time more resistant, and consists mainly in from one, two or more sheet metal plates suitformingv the various parts of the structure ably folded, connected and soldered so as to form a main sleeveon which are subsequently fastened and soldered the connecting tubes which serve for the connection with the secondary elements.

; In the accompanying drawlngs showing 7 schematically and by way of example three embodiments of the object of this invention:

Figures 1 and 2 show a first embodiment partially in view and partially in section respectively, according to two perpendicular planes;

Figures 3 and 4 show a second embodiment in a mannersimilar to the preceding one;

Figures 5 and 6 show in a like way a third embodiment, and

Figures 7 and 8 show the object of the invention applied to the construction of a flat longron represented in side view and in transversal section, respectively.

The attachment is substantially obtained (Figs. 1 and 2) by suitably cutting out a sheet metal piece which is then folded so as to form the cylindrical sleeve 1 with a projecting longitudinal crown or rib obtained by overlapping the two borders 22, which are then soldered autogenously along the superposed borders after having placed. between them a strengthening or thickening piece 1. In this rib are formed the two lugs 3, 3, provided with holes 5, 5 which serve for the passage of the bolts to which are anchored the diagonal stays.

The first sleeve is thus completed, and the location of the second sleeve, normal to the first one, is effected by means of a cylindrical tube 6, provided with two diametrically opposite notches to allow of the passage of rib 2, cut out at the upper portion according to enously soldered.

the intersection of the two cylindrical surfaces, so as to become reclprocally connected.

The borders of tube 6 contacting with or conthogonal among themselves, arranged uponthe two ribs, while the othertwo have reference to an attachment with a sleeve providedwith three ribs, and two connecting tubes arranged upon two of'the ribs each having two lugs, the third rib, to which no connecting tube is applied, having only one lug.

These various embodiments of the attachment serve to renderpossible all the connections which in practice are likely to occur in the different points of tubular structures used in aeronautical constructions, and these 7 embodiments may vary in any way whatever without departing" from the fundamental idea of'the invention.

Figures 7 and 8 show by way of example a flat longron, with two orders of longitu- 8O dinal elements 77, in which are used attachments of the type shown in Figures 1 and 2 for the connection with the transversal tubular elements 8 and the diagonal stays 9.

ld' ith attachments of the type shown in Figures 3 and 4 it is possible to construct prismatic longrons having four longitudinal elements, fuselage bodies and the like and the same is the case with the other embodiments. 9t

Claims:

1. Attachment for the connection of the longitudinal, transversal and diagonal elements of the tubular structures used in aeronautical constructions, consisting in a main sleeve obtained by bending one or more sheet metal plates suitably, cut out, folded and joined together so as to form a cylindrical surface provided with radial ribs having an choring lugs for the diagonal elements, on

' QIAttachment according to claimcl in which, with the object of rendering more resistant the anchorage of the diagonal elements to the lugs'formed in the radial ribs between the sheet metal plates, which form them, are introduced thickening and strengthening plates, cut out according to the shape of the said lugs.

3. Attachment according to claim 1, in which the various connecting parts are joined together along the borders and in those points formed with tubular elements running along the edges, connected with the transversal ele-= 'ments and with the diagonal stays by means of the attachments according to claim 1, and whereby between the sheet metal plates,

which form the lugs in the radial ribs, are

introduced thickening and strengthening plates, cut out according to the shape of the said lugs, and further the various parts are joined together along vthe borders and in those points, in which it is necessary, by

means of autog'enous soldering.

; i In testimony whereof I' have aillxed my signature this 16th day of November, 1929.

' v i-GIANNI CAPRONI.

in which it is necessary, by means of autoge- 'e nous soldering.

4. Flat longron for aeroplane consisting of two longitudinal tubular elements, which by means of the attachments according to claim 1 are connected with the tubular transversal elements and with the diagonal stays.

5. Prismatic V longron for aeroplane formed with tubular elements running along the edges, which by means of the attachments according to claim 1 are connected with the 'transversal elements and with the diagonal 7 stays.

6. Flat longron for aeroplane consisting of two longitudinal tubular elements, which, by means of the at achments according to claim 1, are connected with the tubular transversal elements and with the diagonal stays and whereby between the sheet metal plates, which form the lugs of the radial ribs, are introduc thickening and strengthening plates cut out according to the shape of said lugs. e

7. Flat longron for aeroplane consisting of two longitudinal tubularelements which, by means of the attachments according to claim 1, are connected with the tubular transversal elements and with the diagonal stays and whereby between the sheet metal plates, which form the lugs of the radial ribs, are introduced thickening and strengthening plates, cut out according to the shape of the said lugs and further the various parts are joined together along the borders and in those points in which it is necessary by means of autogenous soldering.

8. Prismatic longron for aeroplane formed with tubular elements running along the edges, connected with the transversal elements andwit-h the diagonal stays by means of the attachments according to claim 1 and whereby between the sheet metal plates, which form the lugs in the radial ribs, are

introduced thickening and strengthening plates, cut out according to the shape of the said lugs. Y

9. Prismatic longron for aeroplane 

